Aviation



C. L. ANDERSON Aug Z39 1927.,

AVIATION Filed June 21, 1924 2 Shams-Sheet l INVENTOR f @@my BV ATTORNEY@Zai Mm Aug 23 1927' c. l.. ANDERSON AVIATION Filed June 21, 1924 2Sheets-Shes?. 2

ma@ K @M1 J @im ATTORNEY Patented Aug. 23, 1927.

VUNT'ED STATES PATENT OFFICE.

CHARLES L. ANDERSON, F RENO, NEVADA.

AVIATION.

Application led .Tune 21,

' reduced to a minimum. Another object is to provide such an airplanecapable of convenient and dependable control during flying and duringascent and descent. Another Objectis to provide a practical and-eiicientart of aviation whereby flying is simplied and the hazards thereof.reduced. Other objects will v be in part :obvious or in part pointedvout hereinafter.'

The invention accordingly consists in the features of construction,combinations of elements, arrangements of parts and in the several stepsand relation and order of each of the same to one or more of the othersall as will be'illustrativel described herein, and the scope of the appication of which will be indicated `in the following claims.

In the accompanying drawings in which is shown one of the variouspossible embodi ments of the mechanical structure of this invention,

Figure 1 is a front elevation of an airplane.

Fgurc 2 is a plan view of the upper portion ot the airplane, the lowerportion thereof being omitted in'order not to en. cumber the drawing.

Figure 3 is a side elevation.

Figure 4 is a section taken substantially along the line 4 4 of Figure1, and

Figure 5 is a section taken substantially along the line 5-5 of Figure1.

Similar reference characters refer to similar parts throughout theseveral views of the drawing.

Referring now to the drawing in detail, there is shown the fuselagewhich may be of any desired type, and containing the opcrators scat 11.In the forward portion of the fuselage 10, in advance of the driversposition 11, is located the motor, the radiatoror" which is indicated at12, the drive shaft 13 projecting therethrough and connected to rotatethe propeller 14. The landing gear 1924. Serial N0. 721,402.

ward wheels 15 connected through suitable shock absorbing devices 16with struts 17 and 18 upon which the fuselage 10 is supported, and atail support comprising a rear wheel 19 suspended from the rear portionof the fuselage 10 by Suitable struts 20 and 21. Pivoted at the rear'endof the fuselage 10 is a vertical controlling rudder 22 which is adaptedto be operated in the usual manl ner through control wires 23 'passingthrough the fuselage 10 to the operators -seat 11.

` The parts thus far described are shown only somewhat diagrammatically,since they may be of usual construction and their details areunimportant as relatingto the dominant features of this invention.

Projecting laterally from either side of the fuselage 10, as best shownin Figure 4, are a pair of parallel frame members 24 and 25 each ofwhichis braced by a pair of frame braces 25 and 27, as shown in Figure l. Theconstruction about to be described is the same on both sides ot thefuselage 10 so that that on one side only will be described in detail,similar reference charactersbeing employed to incieate the similar partson both sides. As shown inv Figure 4, a transverse shaft 28 extendsbetween the two Jframe members 24 and 25 having a bearing in each of thetrame members at 24 and 25a respectively. This shaft 28 extends through.the frame members 24 and 25, and at its ends are secured a pair of bevelgears 29 and 30 respectively. The gear 29 meshes with a gear 30 upon ashaft 31 which is connected through a clutch mechanism 32 in drivingconnection with a bevel gear 33. upon the drive shaft 13 of the motor isa double bevel gear 34 with one face of which the gear 33 coacts.adapted to be `rotated in the direction kindicated by the arrow throughthe clutch 32 'from the drive shaft 13 of the airplane motor.

The gear 30 at the rear end of the shaft 28 meshes with a gear 35 upon ashaft 36 which is connected through a clutch mechanism 37 in drivingrelation with a bevel gear 38. A drive shaft 13"L projects from the rearot' the airplane motor and mounted thereon is a double bevel gear 39with one face of which the bevel gear 38 coacts. The two gears 34 and 39thus, through the respective clutches 32 and 37 and shafts 31 maycomprise, for example, a pair of forand 36, in unison drive the shaft28.

Mounted Rigidly connected to the shaft 28 adjacent its forward end arefour radial arms 40 spaced at 900, and adjacent the rear end of theshaft 28 are rigidly secured four similar and corresponding radial arms41. Vln the ends of corresponding pairs of these arms 40 and 41, arerotatably supported shafts 42 which are parallel to the shaft 28 andeach of which carries a wing or vane 43 rigidly mounted thereon. Thearms 40 and 4l, and hence the wings carried thereby rotate with theshaft' 28 about 'the axis of the shaft 28, as indicated by arrow 44 inFigure 1. Mounted upon the shaft 28 between the arms 40= and the framemember 24, is a hub 45 which comprises four sprockets with each of whichcoacts with one of four chains 46. These chains extend mentheshaftbetuen the arms 41 and dividual axes 42 in a direction oppositetothe revolution and rotation of the wings 43 on. the left-hand sideofthefuselage. VVVThus,

on the downward stroke of the wings, the wings on both sides are movingaway from the fuselage forcing the air downwardly in suchdirectionYastolad'ord'the most advantageous lifting force. The two setsof wings l43 thus driven from the motor serve to lift the airplane inl avertical direction and their drive may be' thrown in or cut out at willby comprising four sprocket wheels, similarI to the sprocket hub 45.Four driving chains 49 connect the `four sprockets of this hub 48 withfour sprockets 50 mounted upon the rear ends of tho tour shafts 42carrying the wings 43. Thus as the wings 43 are rotated about the axisof the shaft 28, they are also rotated by the driving chains 46 and 49about the axes of their respective shafts 42, as indicated by the arrow51 in Figure 1.

The ratio of the sprockets 45 and 47 and oE the sprockets 48 and 50 is'such that the wings 43 are turnedl about their respective axes 180during each rotationof the shaft 28. Furthermore, this connection issuch that on the downward stroke of each wing 43 it is passing throughits :dat-wise position so that it forces air downwardly. This may bestbe realized by reference to Figure 1, wherein it will be seen that thewings 43, when in uppermost position, are substantial ly at an angle ot45 with respect to the horizontal` that when they are half through theirdownward stroke they are substantially horizontal, and in theirlowermost position they are again at substantially 45 with respect tothe horizontal` but tilted in the opposite direct-ion from that in whichthey are tilted. in their uppermost position. On their upward strokesthe wings 43jcut the air substantially edgewise so that little reJsistance is offered during this portion of their rotation. These wings43 therefore revolving about the laxis of the shaft 28 and rotatingabout their individual axes, tend on their downward strokes to force airdownwardly and thus lift the airplane.

Referring again. to Figure 4, the double bevel gears 34 and 39 on themotor drive shaft, with one face of which the gears 33 and 38respectively mesh, serve also to drive through gears 33 and 38a alifting mechamanipulation of the clutches 32 and 37, as will bedescrlbed. Referrlng again to Fig ure 4, connected to operate'the clutch32 1s a lever 52 pivoted to the frame member 24 and connected with a rodv53 extending rear-V wardly along the /uselage 10. A forward movement ofthe rod 53, it will be seen, through the lever 5,2, moves the clutch 32to the position of disengagement. Connected to the lever 52 is an arm 54which is adapted upon such movement of the clutch to slide into lockingengagement with a toothed collar 55 fixed upon the shaft 31. Thus, whenthe rod 53 is operated to disengage the clutch 32, the shaft-31 is atthe same time locked against further lrotation and the wings 43connected in driving relation therewith are also locked against furtherrotation. Connected to operate the clutch 37 is a lever 56 which ispivoted upon an extension 57 from the frame member 25 and which is alsoconnected to the slidable operating rod 53. A forward movement of therod 53, through the lever 56, moves the clutch 37 to the position ofdisengagement and also an arm 58 into engagement with a toothed lockingcollar 59 secured upon the shaft 36. Thus h v manipulation of theoperating rod 53 the clutches 32 and 37 are thrown out of engagement andthe wings 43 are locked against further rotation by the two lockingcollars 55 and 59. r[his clutch release and locking mechanism issubstantially the same on each side ci the `luselage 10 and similarreference characters are employed to indicate similar parts in both. Thetwo slid'- able operating rods 53 may extend rearwardly to a positionadjacent the drivers 'seat 11 as indicated in Figure 3 and be operatedtherefrom as by a suitable handle indicated at 60.

The propeller 14, as indicated, is of a CII 'gegen-lent of Well-knowntype in which the propeller blades are capable of adjustment as to pitchso that they may be set in neutral posit-ion, that is so that thepropeller gives substantially no forward thrust, and the blades may beadjusledas desired to change their pitch and drive the airplane in aforward direction. The control for this adjustmentof the propeller isnot shown herein in order not to encumber the drawings and may be of aWell-known type operated from the drivers position 1l. Thus, theairplane motor may be started and run. freely with the propeller 14 in.neutral position and the clutches 32 and 37 thrown out oi povv'ertransmitting relation, the wings i3 being locked against rotation,Thereupon the operator desiring` to ascend may throw in the clutches and37 by means oi' the levers o0 and the airplane is lifted from the groundby the rapid revolution of the lifting Wings 4,3, Having attained thedesired elevation the operato-r inaytlirow out the clutches 32 and 37,thereby locking the wings 43 against further movement and may thereuponchange the pitch ofthe adjustable propeller to start the propulsion ofthe airplane in a tor'vvarr A direction.

Referringagain to Figure l, there are mountedbetween the two framemembers 24e and :25 on. either side of the vfuselage l0, and adjacentthe-outer ends oi these traine .niembers, a' pair of Wings 5l. These twoWings are substantially similar in construction and control so that oneonly need be described lin detail, similar reference characters beingemployed in the drawings to denote similar parte oi bothg ln Figure 4,the wing 6l on the left-hand side of the fuselage, as viewed in Figure1,'is seen to be mounted upon a 'rod 62 extending therethrough andhaving bearings at its erols in the respective frame members 2li and 25nThe Wing 61 is thus capable of adjustment about the axis of the rod 62.ltsadiustinent in a clockwise direction, as viewed in Figure l., islimited by enlugs 61 thereon with hooked ends of the frame members rnd25, in which position the 'Wing 6l is iu substantially a horizontalplane. The adjustment of the Wing' 6l may be controlled by suitablecontrolling means operated from the-drivers position; `for example,there is diagrammaticaliy shown in the drawing a control comprising apair olf pull wires 63 and 6ft connected to the Wing 6l on oppositesides ot the axis 62, passing over pulleys 65. and GG respectively, andconnected with a shaped operating lever 6?', By swinging the lever 67'about its pivot, the Wine' (il is swung about its axis 62 rom the fullline position shown in Figure 'l to the dotted line position, or .in areverse direction. The wing 81 on the. right-hand side of the fuselage10 is similarly controlled as will be understood by applying the abovedescription to this mechanis Referring now more particularly to Figuresl and 3, there is provided, extending upwardly from the fuselage l0 andfrom the lateral frame members 24 and 25, a suitable frame workcomprising, Afor example, suitably braced forward vframe members (i8 andcorresponding rear trarne members' 69., This traine Work supports at itsupper portion a top Wing 70.V This Win 70 is fixed upon atransverseshaft or rod l, extending there-- through, which shaft is rotatablysupported by the frame Work, for example as indicated at the points 71a,shown best in Figure 2. This wing 7 0 is thus capable of adjustmentabout the axis of' the shaft 7l being adaptid to swing from the fullline position shown in Figure 3 to the. dotted line position and backagain, its swinging being limited by engagement with the frame members72 and 73, as indicated in this figure. In the full line positionagainst the frame member 72 the wing 7 0 is substantially in normalflying psition, its forward end being yslightly tilte up.

Suitable controlling' means is provided :for controlling the adjustmentof the wing 7() from the drivers position 1l. This controlling meansniay take the form, for example. as shown in Figure 5 of pull Wires 74and 75, one connected to the Wing 70 on either side oi' the axis 71 andextending to a vsuitable control lever 75 Within reach of the operator.

As shown in Figure 2, the Wing 71 is provided with suitable-:ailerons 77by means of which the flight of the airplane may be controlled inthe'usual manner when the wing 70 is in normal tlyin position, Thecontrols for these ailerons 7 are not shown since they may be of theusual form operated from the drivers seat in conunction with the tailrudder 22.

Referring again to Figure 3, there is provided at the rear end of thefuselage l0 the usual elovatibn control plane 78 xed upon a pivotallysupported transverse shaft 79n The' elevator 7 8' is thus capable ofadjustment about'its axis 79 and may be adjusted' byy means of controlWires such'as 80 and 8i to any desired angle or to the vertical positionindicated in. dotted lines. The control wires @0 and 8i may, forexample, pass through the fuselage 10,' as 'sliownfand be operated by asuitable operatin lever 82 positioned Wit-hin reach of the driver of theairplane.

In the operation of this machine, the motor is iirst started with thepropeller Mr.

' adjusted to give substantially no forward thrust and with tbe clutches32. and 37 thrown to position of disengagement. The

operator thereupon, by ineens of the oontrols 67, 76 and 82 adjusts thepanels 6l, the

wing 70 and the elevator 7 8 to substantially vertical position asindicated by their respective dotted line positions in Figures 1 and 3.Then, by meansof the levers 60, the clutches 32 and 37 are thrown in,starting the propulsion of the lifting wings 43 which act to verticallyraise the machine into the air,l the center ofmass of the machine beingproperly positioned with respect to the lifting wings 43. During suchascension the panels (il, the Wing `70 andthe elevating plane 78 may bcoperated through their controls if desired to control the upwardmovement of the machine. Having reached the desired altitude, theoperator throws out the clutches 32 and 37 locking the lifting wings45:3 against further revolution, adjusts the panels 61, the wing 70 andthe elevator 78 to normal flying position, and then adjusts the vanes ofthe propeller 11i to start the propulsion of the machine in a forwarddirection. It will be understood that the controls for these adjustmentsmay, if desired, be constructed to operate in unison so that theadjustments accomplished substantially simultaneously, the controlsshown herein being only diagrammatically represented.

Elevation having been attained and the forward propulsion of the machinestarted, as above described, the iying of the airplane nesasss set forthor shown in the accompanying drawings is to be interpreted asillustrative and not in a limiting sense.

l claim as my invention:

1.. in an aerial machine, in combination,

an airplane body, a motor mounted adjacent the forward end thereof,lateral frame members extending outwardly from said body adjacent saidmotor, a horizontal shaft rotatably mounted in said frame members, aplurality of wings spaced about said shaft and connected therewith torevolve therewith about the axis of said shaft, saidv wings beingrotatably mounted about individual axes substantially parallel to theaxis. of said shaft, driving means connecting said shaft and 'said wingsadapted during rotation of said shaft and revolution of said wingsthereabout to rotate said wings about their individual axes so that upondownward movement they cut the air Substantially fiatwise tending tolift the airplane and so that upon upward movement they cut the airsubstantially edgewise, a driving shaft extending outwardly from saidbody along said frame members having adjacent its outer end a drivingconnection with said transverse shaft and at its inner end a clutchconnection with the drive shaft of said motor, mea-ns for operating saidclutch to control the drive of said horiay-be Y controlled Yin Y thesausti-elem annerehysontalsh afteandsaidwingsfe means of the ailerons77, the tail rudder 22 and the elevating plane 78, The panels 6l and thewing 70 are designed to afford sumcient lifting surface to support theairplane in ordinary flying. When it is desired to descend the drive ofthe propeller 14 may again be interrupted, and the forward momentum ofthe machine havin@i decreased, the clutches 32 and 37 may be thrown into actuate the revolving wings 43, the speed of revolution of which bycontrol of the speed of the motor may be so controlled that the wingspermit gradual descent of the machine. During such descent thepanels-61, the wing 70 and the elevatory78 may be f' turned'to controithedirection 'ofthedown" YWrapidvtaiting"oliucrviandingvarevdonevawayvdrivingvshafts with.' Furthermore, theseadvantages are attained without sacrifice of the practicability andoperativeness of the machine for flying.

As many possible embodiments may be made of the mechanical features ofthe above invention and as the art herein described might be varied invarious parts all without departing from the scope of the invention, itis to be understood that all matter herein adapted upon disengagement ofsaid clutch to loch said outwardly extending driving shaft and saidwings against further rotation.

2. In an aerial machine, in combination, an airplane body, a motormounted adjacent the forward end thereof, lateral frame membersextending outwardly from said body adjacent said motor, a horizontalshaft rotatably mounted in said frame members, a plurality of wingsspaced about said shaft and connected therewith to revolve therewithabout the axis of said shaft, said wings being rotatably mounted aboutindividual axes substantially parallel to the axis of said shaft,driving means connecting said shaft and said'mwings adapted duringrotation of said shaft and revolution of said wings thereabout 'torotate said wings about their individual axes so 'that upon downwardmovement they out the VairY substantially yiiatwise tending Vto liftYthe airplane and so that upon upward movement they cut the airsubstantially edgewise, a pair of extenuhmoutwarvy"from said body alongsaid frame members having adjacent their outer ends driving connectionswith said horizontal shaft and at their inner ends clutch connectionswith ythe drive shaft of said motor, and means for jointly operatingsaid clutches to control the drive of said horizontal shaft and of saidwings, and means adapted upon disengagement of said clutches to locksaid wings against further movement.

3. In anaerial macbine, in combination, an airplane body, a motormounted adjacent the forward end thereof, lateral frame membersextending'outwardly from said body adjacent said motor, a horizontalshaftrotatably mounted in said frame members, a plurality of wingsspaced about said shaft and connected therewith to revolve therewithabout the axis of said shaft, said wings being rotatably mounted aboutindividual axes substantially parallel to the axis of said shaft,driving means connecting said shaft and 'said wings adapted duringrotation of said shaft and revolution of said wings thereabout to rotatesaid wings about their individual axes so that uJ on downward movementtbey out the air su stantially llatwise tending to lift the airplane andso that upon upward movement they out tbe air sub stantially edgewise,a. driving shaft enteruling outwardly from said body along said framemembers having adjacent its outer end a driving connection with saidhorizontal shaft and at its inner end :a clutch. oonnection with tbeforward end of vtbe drive shaft of said motor, a second driving shaftextending outwardly from said body along said frame members havingadjacent vits outer end a driving connection with said.

horizontal shaft and at its inner end a clutch connection wit-ll `1 therear end of the drive shaft of said i otor, and means for jointlyoperating said two clutches to control the drive of said horizontalshaft and said wings. j Y

4. In anfaerial machine, in combination, an airplane body, a motormounted adjacent the forward end thereof, a propeller adapted to bedriven. by saidinotor to propel said airplane in a forward direction,lateral frame members extending outwardly from lsai-d body adjacent saidmotor, supporting wings at the outer end portions of said frame members,means supported by said frame finembers between said body and said wingsadapted to propel said airplane in an upwaid direction, means foradjusting said supporting wings substantially from a 'horizontal planeto a vertical plane to guide the airplane in its upward flight, and anelongated supporting wing extending transversely'of said body above saidupward propelling means and above said rst supporting wings forsupporting said airplane in forward flight.

5u ln an aerial machine, in combination, an airplane body, a motormounted adjacent the forward end thereof, a propeller driven from saidmotor adapted to propel said airplane in a forward direction, lateralframe members extending outwardly from said body adjacent said motor,supporting wings adjacent tbe outer ends of said frame mem bers, meansdriven from said motor and su ported by said frame members between said6, In an aerial machine, in combination,

an airplane body, a motor mounted adjacent the forward end thereof.,lateral frame members extending outwardly from sa id body adjacent saidmotor, horizontal shaft rotatably mounted in said frame members, a

plurality of wings spaced about said shaftand connected therewith toI.revolve therewith about the axis of said shaft, said wings beingrotatably mounted about individual .axes substantially parallel to theaxis of said shaft,ldriving 'means connecting said shaft and said wingsadapted during rotation of said shaft and revolution of said wingstbereabout to rotate said wings about their individual axes so that upondownward movement `they out the air substantially flatwise tending tolift the airplane and so 'that upon upward movement they cut the airsubstantially edgewise, means for driving said horizontal shaft fromsaid motor, a propeller driven from said motor adapted to propel saidairplane in a forward direction, sup-l porting wings positioned at tbeouter ends of said lateral frame members exterior of said rotatingwings, means for independently rendering effective said drive of saidhorizontal shaft and said drive of said propeller, and means foradjusting said supporting wings. substantially from a horizontal planeto a vertical plane. l

7, In an aerial machine, in combination,

an elongated airplane body, a motor niouuted adjacent the forward endthereof, a propeller vdriven from said motor adapted to propel saidairplane in a forward direction, a supporting ring extendingtransversely of said body and spaced yabove the same adjacent tbeforward end thereof, and reaching to a substantial distance on eitherside thereof, frame members extending laterally from said body adjacentsaid motor, means supported by said frame members beneatli saidsupporting wing adapted to be driven from said motor to propel saidairlane in an 'upward direction, and means or adjusting said entiresupporting wing about an axis-extending transversely of said bodysubstantially 'from a horizont-al plane 'to a vertical plane tofacilitate upward glit of said airplane, and additional means orhguidingsaid airplane in its upward In an aerial machine, in combination,

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an elongated airplane body, a. motor supported adjacent the forward endthereof, a propeller driven. from said motor adapted to propel saidairplane in a forward direc* tion, a supporting wing extendingtransversely of said body and spaced above the same adjacent said motor,and reaching to a substantial distance on either side thereof, saidsupporting wing being throughout its entire length supported upon ahorizontal axis extending substantially through the renter thereoftransversely of said body, frame members extending laterally from saidbody adjacent said motor, means supported by said frame menbers beneathsaid supporting wing adapted to be driven yfrom said motor to propelsaid airplane in an upward direction, means for rendering independentlyoperative the drive of said propeller and the drive of said upwardly propeiling means, and means lfor adjusting the position of said supportingwing about its axis substantially fro-iii a horizontal plane to avertical plane to facilitate the upward flight of the airplane.

9. ln an aerial machine, in combination, an airplane body, a motormounted. adjacent the forward end thereof, a propeller driven from saidmotor adapted to propel said airplane in a forward direction, asupporting Awing extending transversely of Said body adjacent theforward end thereof and spaced upwardly therefrom, frame membersextending laterally from said body adjacent said motor, supporting wingsadjacent the outer ends of said frame members, and beneath saidfirstsupporting wing, means supported by said frame membersv betweensaid body and said last supporting wings adapted to be driven from saidmotor 'to propel said airplane in an upward direction, means forindependently rendering effective the drive of said propeller and saidupwardly propelling means, and means for adjusting said first supportingwing and said last supporting wings substantially from a horim zontalplane to a vertical plane.

10. In an aerial machine, in combination,

an airplane body, a motor mounted adjacent the forward end thereof, apropeller adapted to be driven from said motor to propel said airplaneinV a forward direction, lateral frame members extending outwardly fromsaid body adjacent said motor, a horizontal shaft rotatably mounted insaid frame menihers, a plurality of wings spaced about said shaft andconnected therewith to revolve therewith about the axis of said shaft,said wings being rotatably mounted about individual axes substantiallyparallel to the axis of said shaft, driving meansconnecting said shaftand said wings adapted during rota.- tion of 'said shaft and revolutionof said wings tliereabout to rotate said wings about their individualaxes so that upon down-y ward movement they cut the air substantiallyflatwise to lift the airplane and so that upon upward movement they cutthe air substantially edgewise, a driving shaft. eX- tending outwardlyfrom said body along said frame members having adjacent its outer end adriving connection with said transverse shaft and at its inner end aclutch connection. with the drive shaft of said motor, means for'operating said clutch to render the drive of said wings operative `orinoperative, means adapted upon disengagement of said clutch to lock;said wings against further rotation, a supporting wing extendingtransversely of said body and spaced upwardly above saidrot-ating wings,

means for adjustingthe position of said. supporting wing substantiallyfrom a hori-l zontal position to a vertical position to faw cilitateupward movement of said airplane, a supporting wing mounted in saidframe members beneath said first wing and eX- terior of said rotatingwings, and means for adjusting said last wing substantially from ahorizontal plane to a vertical plane for guiding said airplane in itsupward movement,

In testimony whereof, I have signed my name to this speciiication this29th day of May, 1924.

CHARLES L. ANDERSON.

